JP2009503482A - Testing equipment for fuselage structure with longitudinal and circumferential curvature - Google Patents

Abstract

  A test apparatus for a fuselage structure (10) having longitudinal and circumferential curvatures comprises a group of means (60, 80) for applying a force to the fuselage structure. The test apparatus includes a central axis (20) configured to extend in the longitudinal direction at the center of the fuselage structure and to be coupled to the fuselage structure (10). A group of means for applying force is mounted between the fuselage structure and support means (70, 90) connected to the central shaft (20). This test device is used in particular for testing aircraft fuselage.

Description

  The present invention relates to a test apparatus for a fuselage structure having a double curvature.

  More specifically, an object of the present invention is to provide a test apparatus capable of performing fatigue and proof static tests on a fuselage structure having a double curvature, that is, a longitudinal curvature and a circumferential curvature.

  In practice, such a fuselage structure is an annular fuselage that is commonly utilized to be implemented at the rear or front of an aircraft fuselage.

  It is known to use such test equipment to apply stresses to the fuselage structure that correspond to the stresses experienced by the fuselage structure in use from the system that applies the force. Stress is generally a pressure related to the tensile and compressive forces exerted along the length of the structure, torsional forces along the perimeter of the structure, and the pressure differential that exists between the interior and exterior of the aircraft. is there.

  For example, a test apparatus capable of applying pressure and an axial mechanical load to a cylindrical structure having a simple curvature is known. It is described, for example, in M. Langon and C. Meyer's "Development of a fixing device for testing curved panels like a fuselage", CEAT, ICAF, 1999, pages 745-753.

  However, such a test device cannot be applied to a fuselage structure having a double curvature while maintaining the actual stress experienced by the aircraft fuselage structure.

  An object of the present invention is to solve the above-mentioned drawbacks and to provide a test apparatus for a fuselage structure having a double curvature.

  To that end, a fuselage structure testing device having curvatures in the longitudinal and circumferential directions comprises a group of means for applying forces to the fuselage structure.

  In accordance with the present invention, the test apparatus includes a central axis that is in the center of the fuselage structure, extends in the longitudinal direction, and is coupled to the fuselage structure. A group of means for applying force is mounted between the fuselage structure and support means connected to the central shaft.

  Therefore, the test apparatus of the present invention has a central axis that can realize a firm structure at the center of the fuselage structure and can reproduce the stress applied to the fuselage structure.

  Thanks to the ability to reproduce stress at the center of the fuselage structure, the space outside the fuselage structure can be freely used, so that the stressed fuselage structure can always be inspected.

  According to one embodiment of the present invention, the test apparatus includes a connecting means configured to connect the central axis to the upper end portion of the fuselage structure, and the means for applying force is configured to exert a force on the lower end portion of the fuselage structure. is there.

  With this configuration, torsional stress or tensile stress / compressive stress can be applied to the entire body structure. The stress applied between the upper end portion and the lower end portion of the fuselage structure can be reproduced by the central axis.

  According to one embodiment of the present invention, the support means supports a pedestal plate configured to support the first type means for applying force and a second type means for applying force applied to the central axis. It is equipped with the foundation of the structure to do.

  Thus, the two types of applied forces can be separated so that the applied forces can be varied independently during testing, and results on the fuselage structure are analyzed uncorrelated with respect to the different types of forces applied can do.

  In practice, the first type of means for applying force is a configuration that applies a torsional force to the fuselage structure, and the second type of means for applying force is a configuration that applies a tensile or compressive force to the fuselage structure. It is.

  The first type of means for applying the force is preferably capable of applying a force directed in the tangential direction of the curved surface of the body structure.

  Since the force applied in this way can remain on the same straight line (collinear colineaire) as the surface, the surface can be deformed.

  In practice, the first type of means for applying force comprises at least one jack. The jack is configured to apply a force along a horizontal axis, and is attached so as to be able to rotate about a vertical axis at both ends.

  Thanks to the jacks being pivotally mounted in this way, the torsional force exerted on the surface of the fuselage structure is tangential to the surface even after the surface is displaced or deformed. Ingredients are always preserved. In practice, the means for applying the force is connected to the load transmission ring in order to apply the force for the purpose of regularly applying a force to the body structure. At that time, the lower end portion of the body structure is fixed to the load transmission ring.

  Other features and advantages of the present invention will appear in the following description.

  The accompanying drawings are presented by way of example.

  An embodiment of a test apparatus for a fuselage structure will now be described with reference to the drawings.

  A fuselage structure 10 having a double curvature as shown in FIG. 1 can be tested by a test apparatus described below.

  As shown by the arrows in FIG. 1, an annular body having both a longitudinal curvature and a circumferential curvature is problematic.

  This test apparatus can perform a static test of tolerance to fatigue and fracture on such a structure.

  In general, this test equipment is subject to stresses experienced by the structure of the aircraft, in particular, longitudinal tensile or compressive forces, or torsional forces on the long axis, or pressures due to pressure differences between the interior and exterior of the structure. Corresponding stress can be applied.

  Of course, these types of forces need to be combined to affect the fuselage structure.

  2 and 3 show an entire test apparatus according to an embodiment of the present invention.

  At present, the behavior of fuselage structures with double curvature is understood with the help of tests and numerical simulations on structures with simple curvature.

  Therefore, test data is required to confirm and calibrate the numerical model used in the fuselage structure to understand the behavior of a fuselage structure with double curvature.

  With the test equipment described below, the behavior of new materials (metals and composites) can be evaluated and studied, and new technologies can be studied.

  This test apparatus is provided with a central axis 20 that is essentially in the center of the fuselage structure 10 and extends in the longitudinal direction.

  The central shaft 20 includes a pedestal 21 fixed to the ground and a vertical bar-like member 25.

  The pedestal 21 is particularly shown in FIG. The pedestal 21 includes a portion that forms a base portion 22. The base portion 22 is fixed to the pedestal plate 70 by a series of screws 22a as shown in FIG. The pedestal plate 70 will be described later.

  The pedestal 21 has a cylindrical outer shape as a whole, and includes an annular portion 21a. The annular portion 21a forms a shoulder portion 21b with respect to the cylindrical trunk portion 24 of the pedestal 21. The attachment of the means for applying force to the shoulder 21b will be described later.

  The pedestal 21 can be lightened by the cylindrical central punching portion 21c.

  A disk-shaped end face 23 on the side opposite to the base 22 of the pedestal 21 is provided with means for connecting the pedestal 21 to the vertical rod-like member 25. In this embodiment, the pedestal includes a groove 23b extending along the diameter of the disc-shaped end face 23. The groove 23b is configured to cooperate with a complementary rib (not shown) provided on the end surface 25a of the bar member 25 in the vertical direction as shown in FIG.

  Of course, a connection means opposite to this may be provided between the base 21 and the rod-like member 25. Alternatively, another type of connecting means that provides the structure of the central shaft 20 with sufficient strength to withstand the stress applied to the body structure 10 may be provided.

  The vertical rod-shaped member has a diameter of 1 m and a height of about 4 m, for example. Of course, the height of the vertical bar can be varied depending on the length of the fuselage structure to be tested.

  The pedestal 21 and the vertical rod-like member 25 are, for example, cast structures, which are machined and can support and reproduce the stress applied to the trunk structure.

  The rod member 25 in the vertical direction includes connecting means 30 and 40 at one end 27, and the connecting means 30 and 40 connect the central shaft 20 to the upper end portion 10 a of the body structure 10.

  As can be seen from FIG. 8, the connecting means includes a lid 30 connected to the upper end portion 27 of the central shaft 20.

  This fixation of the lid 30 to the central shaft 20 must be strong enough to withstand the torsional forces exerted on the fuselage structure 10 and tensile or compressive forces. Therefore, the central axis 20 can reproduce the stress that the fuselage structure receives.

  Therefore, in this embodiment, the upper end portion 27 of the rod member 25 in the vertical direction is provided with a series of grooves 28 extending in parallel with the axis of the central axis 20, and the series of grooves is provided on the inner surface 30a of the lid 30. Fit into a series of complementary grooves 31.

  Actually, the lid 30 includes a cylindrical body portion 32 having an internal punching hole 33 having a cylindrical shape as a whole. A complementary groove 31 is provided on the inner surface of the internal punching hole 33.

  These grooves are particularly suitable for reproducing the torsional stress of the lid 30 with respect to the end portion 27 of the bar-like member 25 in the vertical direction.

  In order to connect the central shaft 20 with the lid 30 for tension / compression, a series of fixing screws are mounted between the bottom of the lid 30 and the end 27a of the end 27 of the vertical bar 25. .

  Outside the lid 30 is also a series of ribs 35 disposed between the cylindrical body 32 of the lid 30 and the flange 36. These ribs 35 can reinforce the structure of the lid 30.

  Considering the existing forces, and also considering the existence of numerous fixing means for connecting the lid 30 with the vertical rod-like member 25, it is important that the central axis is realized with a solid material. is there.

  Fixing means 40 for fixing the upper end portion 10a of the body structure 10 is provided on the lower surface of the flange 36 of the lid 30.

  As can be seen from FIGS. 9a, 9b, 10a, and 10b, the fixing means 40 is composed of an outer ring 41 and an inner ring 42, and holds and holds the upper end portion 10a of the fuselage structure 10 (in particular, (See Figure 3).

  More specifically, the fixing rings 41 and 42 are generally cylindrical. The outer ring 41 for fixing includes a flange 43, for example. The flange 43 contacts the flange 36 of the lid 30 and is fixed to the flange 36 by a series of fixing screws. Extending from the flange 43 is a frustoconical portion 44 having a shape coinciding with the outer surface of the upper end portion 10a of the body structure 10.

  Similarly, the inner ring 42 for fixing includes a flange 45 fixed to the flange 36 of the lid 30 with a fixing screw, for example. Extending from the flange 45 is a frustoconical portion 46 having a shape coinciding with the inner surface of the upper end portion 10a of the body structure 10.

  Therefore, when the fixing rings 41, 42 are fixed to the lid 30, the fixing inner ring 42 extends inside the frustoconical part 44 of the fixing outer ring 41, and the ring frustoconical parts 44 and 46 are the fuselage. The upper end 10a of the structure can be sandwiched.

  The same attachment method is realized at the lower end 10b of the body structure thanks to the fixing means connected to the load transmission ring 50.

  The lower end portion 10b of the fuselage structure 10, like the upper fixing means 40, is complementary to each other and includes two rings 41 and 42 that define a space for holding the lower end portion 10b of the fuselage structure 10 between the two cylindrical ring portions. It can be clamped in between.

  The means 60, 80 for applying force will now be described with particular reference to FIGS. The means for applying force 60, 80 are attached to support means connected to the central shaft 20.

  As already pointed out, this support means comprises a pedestal plate 70. This can be seen well in FIG. 2, in which the pedestal plate 70 is triangular.

  The pedestal plate 70 is configured to support a first type means 60 for applying a force. This first type of means for applying a force is here a means configured to apply a torsional force to the fuselage structure 10.

  Further, the support means includes a base 90 fixed to the central shaft 20 (the pedestal 21 in this embodiment). The foundation 90 is configured to support a second type of means 80 for applying force. This second type of means for applying a force is here a means of applying a tensile or compressive force to the fuselage structure 10.

  Actually, in this embodiment, three jacks 61 configured to apply a torsional force are provided. These jacks are attached to support members 62 arranged at an angle of 120 ° to each other, and are fixed to, for example, the apex of the triangular pedestal plate 70. These jacks are, for example, hydraulic jacks that exert a force along the piston shaft.

  In order to securely fix the jack 61 to the pedestal plate 70, the support member 62 includes two support columns 62 a that are inclined by 45 ° to 80 ° with respect to the pedestal plate 70. The angles formed by these columns 62a are 60 ° to 90 °.

  The load transmission ring 50 to which the fuselage structure 10 is fixed so as to be complementary to it is composed of three fixing members 58, which are also arranged at an angle of 120 ° to each other, as can be seen from FIGS. 5a and 5b. Have.

  The load transmission ring 50 has a flat shape and is generally triangular. The fixing member 58 is disposed at the apex of this triangle. The load transmission ring 50 further has a circular opening 59 through which the central shaft 20 (particularly, the cylindrical body 24 of the base 21) can pass.

  Each hydraulic jack 61 is horizontally disposed between the support member 62 and the fixing member 58. One end of the shaft of each jack 61 is connected to the fixing member 58 by a screw and a U link, for example.

  Since the other end of each jack 61 is similarly attached, the jack can be connected to the support member 62. Thanks to this attachment using U-links, both ends of the jack can be rotated about two vertical axes in the attachment position relative to the support member 62 and the fixing member 58, respectively.

  Therefore, when the load transmission ring 50 rotates and moves due to the force applied from each hydraulic jack 61, the jack 61 also rotates along with it, so that the jack 61 maintains the direction of action facing the tangential direction of the surface of the body structure. .

  The force applied by each hydraulic jack is now exerted in the same horizontal plane as the plane in which the load transfer ring 50 extends. The force exerted in this way is directed tangential to the surface of the fuselage structure and corresponds to the torsional force exerted on three points equidistant from the load transmission ring. This force is therefore exerted uniformly on the load transfer ring 50.

  Simultaneously with these means by which torsional forces can be exerted on the fuselage structure, six hydraulic jacks 81 arranged between the load transmission ring 50 and the base 90 are also provided.

  As can be understood from FIGS. 6a and 6b, the base 90 has a circular ring shape as a whole, and a circular opening 91 through which the central shaft 20 (in particular, the cylindrical body 24 of the base 21) can be passed. Have

  The base 90 includes a cylindrical side 92 and an annular edge 93.

  As can be seen from FIG. 3, the base 90 has an annular edge 93 resting on the shoulder 21 b of the pedestal 21. Accordingly, the cylindrical side portion 92 defines a housing between the annular portion 21a and the base portion 22 of the base 21. The housing accommodates a bearing capable of attaching the base 90 to the base 21.

  On the annular edge 93 of the base 90, six jacks 81 facing in the vertical direction are attached at equal intervals around the axis of the central shaft 20 facing in the vertical direction.

  Therefore, these hydraulic jacks 81 are arranged on the circular base 90 at an angle of 60 ° with respect to each other.

  As can be clearly understood from FIG. 12, the end of the shaft of the hydraulic jack 81 is fixed to the load transmission ring 50 that supports the body structure 10.

  Since the jack 81 facing in the vertical direction is arranged in this manner between the base 90 and the load transmission ring 50, the tensile force or compression force in the vertical direction passes through the load transmission ring 50 and the lower end 10b transmits this load. The fuselage structure 10 is fixed to the ring 50. The applied force is therefore evenly distributed to the lower end 10b of the fuselage structure 10.

  The horizontal hydraulic jack 61 is thus attached to the triangular support plate 70, while the vertically oriented jack 81 is thus attached to the base 90, so that the applied tensile / compressive force and The torsional forces can be made uncorrelated with each other.

  Furthermore, a pressure generating means 100 is disposed between the central shaft 20 and the fuselage structure 10 so that the pressure difference existing between the interior and the exterior of the fuselage structure 10 can be reproduced and tested.

  In this embodiment, the pressure generating means 100 is constituted by a truncated cone structure 100 located between the vertical rod-like member 25 and the body structure 10. The space between the frustoconical structure 100 and the fuselage structure 10 can be pressurized by sending pressurized air or by an inflatable balloon filled with water.

  For this purpose, an inlet 101 for pressurized fluid is provided. The position is preferably at the bottom of the frustoconical structure 100.

  Accordingly, the frustoconical structure 100 forms a receiving portion that can reduce the space between the central shaft 20 and the body structure.

  Thanks to various means of applying force, any mechanical stress corresponding to the actual behavior of the fuselage structure can be applied to the fuselage structure.

  In particular, the following maximum stress can be applied.

  Furthermore, from the view described above for the device, the outer space of the fuselage structure 10 is in a freely usable state as shown in FIG. 2, so that the fuselage structure can be examined from the outside.

  When fixing the fuselage structure by tightening, the fuselage structure can be easily disassembled and the interior of the fuselage structure can be examined after applying stress.

  Thanks to the modular structure consisting of a pedestal and a vertical bar-shaped member, the central axis can be adapted to various body structures with different heights, especially by exchanging the vertical bar-shaped members.

  In addition, it should be noted that the conventional use of non-destructive inspection methods and the use of sensors pre-arranged at various positions on the fuselage structure eliminates the need to disassemble the fuselage structure during testing.

  By this test method, a fuselage structure having a double curvature can be subjected to a static test for tolerance to damage and fatigue. In particular, the stress applied to the fuselage structure 10 that is recorded thanks to the strain gauge can be measured and any displacement in any direction of the fuselage structure can be observed.

  Of course, the invention is not limited to the embodiments described above.

  In particular, there is no limit to the number of hydraulic jacks used to apply torsional force and to apply compressive or tensile force. Furthermore, means other than a hydraulic jack may be used as means for applying force.

  Furthermore, methods other than the fastening described above could be used to fix the ends of the fuselage structure.

It is a perspective view of the fuselage structure which has a double curvature. 1 is a perspective view schematically showing a test apparatus according to an embodiment of the present invention. FIG. 3 is a longitudinal sectional view of the test apparatus shown in FIG. FIG. 3 is a perspective view of a support for a central axis of the test apparatus shown in FIG. FIG. 3 is a perspective view of a load transmission ring of the test apparatus shown in FIG. FIG. 3 is a top view of a load transmission ring of the test apparatus shown in FIG. FIG. 3 is a perspective view of a base of the test apparatus shown in FIG. FIG. 3 is a cross-sectional view of the base of the test apparatus shown in FIG. FIG. 3 is a perspective view of a core part of a central axis of the test apparatus shown in FIG. FIG. 3 is a perspective view of a connecting lid of the test apparatus shown in FIG. FIG. 3 is a perspective view of a fixing outer ring of the test apparatus shown in FIG. FIG. 3 is a cross-sectional view of a fixing outer ring of the test apparatus shown in FIG. FIG. 9b is a perspective view of a fixed inner ring configured to cooperate with the fixed outer ring shown in FIGS. 9a and 9b. FIG. 9b is a cross-sectional view of a locking inner ring configured to cooperate with the locking outer ring shown in FIGS. 9a and 9b. It is the figure seen from the state in which there is no core part and trunk structure of a central axis, and shows how to attach a means to apply force. FIG. 3 is a partial longitudinal cross-sectional view of the test apparatus shown in FIG. 2, showing how to attach a means for applying force.

Claims (11)

A test apparatus comprising a group of means (60, 80) for applying a force to a fuselage structure for testing a fuselage structure (10) having longitudinal and circumferential curvatures,
The test apparatus comprises a central shaft (20) extending in the longitudinal direction at the center of the fuselage structure (10) and configured to be coupled to the fuselage structure (10);
A group of means (60, 80) for applying the force is mounted between the body structure (10) and support means (70, 90) integrated with the central shaft (20). Test equipment.   It comprises connecting means (30, 40) configured to connect the central axis to the upper end (10a) of the fuselage structure (10), and the group of means (60, 80) for applying the force comprises the fuselage structure 2. The test apparatus according to claim 1, wherein a force can be applied to the lower end (10b) of the test apparatus. A pedestal plate (70) configured to support the first type means (60) for applying force to the support means;
The base (90) comprises a base (90) fixed to the central axis (20) and configured to support a second type of means (80) for applying force. The test apparatus according to claim 1 or 2.   The first type means (60) for applying a force is configured to apply a torsional force to the body structure (10), and the second type means (80) for applying a force is the body structure. 4. The test apparatus according to claim 3, wherein a tensile force or a compressive force is applied to (10).   5. The test apparatus according to claim 4, wherein the first type means for applying force is configured to apply a force directed in a tangential direction of the curved surface of the body structure.   The first type means for applying a force comprises at least one jack configured to apply a force along a horizontal axis, the jack being pivotable about a vertical axis at both ends. 6. The test apparatus according to claim 5, wherein the test apparatus is attached as follows.   A group of means (60, 80) for applying the force is connected to a load transmission ring (50) at the point of applying the force, and a lower end (10b) of the fuselage structure (10) is connected to the load transmission. 7. The test device according to claim 1, wherein the test device is fixed to a ring (50).   The connecting means includes a lid (30) connected to the upper end (27) of the central shaft (20) and a fixing means (40) for fixing the upper end (10a) of the body structure (10). 8. The test apparatus according to claim 1, wherein the test apparatus is characterized in that:   9. The fixing means (40) according to claim 8, characterized in that it comprises an outer ring (41) and an inner ring (42) configured to hold the upper end (10a) of the fuselage structure (10) by tightening. The test apparatus described.   The upper end portion (27) of the central shaft (20) is provided with a series of grooves (28) extending in parallel to the axis of the central shaft (20), and the series of grooves (28) is formed on the lid (30). The test device according to claim 8 or 9, characterized in that it fits in a complementary series of grooves (31) provided on the inner surface (30a) of the same.   The test according to any one of claims 1 to 10, further comprising pressure generating means (100) configured to be disposed between the central axis (20) and the fuselage structure (10). apparatus.

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